Purpose

This paper aims to focus on calculating the number of layers of composite laminates required to take the applied load made up of graphite/epoxy (AS4/3501-6) which can be used in many industrial applications. Optimization for minimization of weight by variation in the mechanical properties is possible by using different combinations of fiber angle, number of plies and their stacking sequence.

Design/methodology/approach

Lots of research studies have been put forth by aerospace industry experts to improve the performance of aircraft wings with weight constraints. The orthotropic nature of the laminated composites and their ability to characterize as per various performance requirements of aerospace industry make them the most suitable material. This leads to necessity of implementing most appropriate optimization technique for selecting appropriate parameter sets and material configurations.

Findings

In this work, exhaustive enumeration algorithm has been applied for weight minimization of fiber laminated composite beam subjected to two different loading conditions by computing overall possible stacking sequences and material properties using classical laminate theory. This combinatorial type optimization technique enumerates all possible solutions with an assurance of getting global optimum solution. Stacking sequences are filtered through Tsai-Wu failure criteria.

Originality/value

Finally, through the outcome of this optimization framework, eight different combinations of stacking sequences and 24-ply symmetric layup have been obtained. Furthermore, this 24-ply layup weighing 0.468 kg has been validated using finite element solver for given boundary conditions. Interlaminar stresses at top and bottom of the optimized ply layup were validated with Autodesk’s Helius composites solver.

中文翻译：

---

使用穷举算法和数值建模的飞机机翼结构纤维叠层复合梁的重量最小化

目的

本文旨在重点计算可用于许多工业应用的由石墨/环氧树脂 (AS4/3501-6) 组成的施加负载所需的复合层压板的层数。通过使用纤维角度、层数及其堆叠顺序的不同组合，可以通过机械性能的变化来优化重量以实现最小化。

设计/方法/方法

航空航天工业专家已经提出了大量研究，以提高具有重量限制的飞机机翼的性能。层压复合材料的正交各向异性特性以及它们根据航空航天工业的各种性能要求进行表征的能力使其成为最合适的材料。这导致需要实施最合适的优化技术来选择合适的参数集和材料配置。

发现

在这项工作中，通过使用经典层压理论计算整体可能的堆叠顺序和材料特性，将穷举枚举算法应用于两种不同加载条件下的纤维层压复合梁的重量最小化。这种组合类型的优化技术列举了所有可能的解决方案，并确保获得全局最优解决方案。堆叠序列通过 Tsai-Wu 失效标准进行过滤。

原创性/价值

最后，通过这个优化框架的结果，得到了八种不同的堆叠顺序和 24 层对称叠层组合。此外，这个重 0.468 kg 的 24 层叠层已经使用有限元求解器在给定的边界条件下进行了验证。使用 Autodesk 的 Helius 复合材料求解器验证了优化铺层顶部和底部的层间应力。